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Research Papers

A Mixed-Fidelity Numerical Study for Fan–Distortion Interaction

[+] Author and Article Information
Yunfei Ma

Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
e-mail: ym324@cam.ac.uk

Jiahuan Cui

School of Aeronautics and Astronautics,
ZJU-UIUC Institute,
Zhejiang University,
Zhejiang 310007, China
e-mail: jiahuancui@intl.zju.edu.cn

Nagabhushana Rao Vadlamani

Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
e-mail: nrv24@cam.ac.uk

Paul Tucker

Professor
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
e-mail: pgt23@cam.ac.uk

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received June 26, 2018; final manuscript received July 11, 2018; published online August 20, 2018. Editor: Kenneth Hall.

J. Turbomach 140(9), 091003 (Aug 20, 2018) (10 pages) Paper No: TURBO-18-1136; doi: 10.1115/1.4040860 History: Received June 26, 2018; Revised July 11, 2018

Inlet distortion often occurs under off-design conditions when a flow separates within an intake and this unsteady phenomenon can seriously impact fan performance. Fan–distortion interaction is a highly unsteady aerodynamic process into which high-fidelity simulations can provide detailed insights. However, due to limitations on the computational resource, the use of an eddy resolving method for a fully resolved fan calculation is currently infeasible within industry. To solve this problem, a mixed-fidelity computational fluid dynamics method is proposed. This method uses the large Eddy simulation (LES) approach to resolve the turbulence associated with separation and the immersed boundary method (IBM) with smeared geometry (IBMSG) to model the fan. The method is validated by providing comparisons against the experiment on the Darmstadt Rotor, which shows a good agreement in terms of total pressure distributions. A detailed investigation is then conducted for a subsonic rotor with an annular beam-generating inlet distortion. A number of studies are performed in order to investigate the fan's influence on the distortions. A comparison to the case without a fan shows that the fan has a significant effect in reducing distortions. Three fan locations are examined which reveal that the fan nearer to the inlet tends to have a higher pressure recovery. Three beams with different heights are also tested to generate various degrees of distortion. The results indicate that the fan can suppress the distortions and that the recovery effect is proportional to the degree of inlet distortion.

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References

Xie, Z. , Liu, Y. , Liu, X. , Sun, D. , Lu, L. , and Sun, X. , 2017, “Computational Model for Stall Inception and Nonlinear Evolution in Axial Flow Compressors,” J. Propul. Power, 34(3), pp. 720–729. [CrossRef]
Tucker, P. , and Liu, Y. , 2006, “Turbulence Modeling for Flows Around Convex Features,” AIAA Paper No. AIAA 2006-716. http://highorder.berkeley.edu/proceedings/aiaa-annual-2006/paper1241.pdf
Liu, Y. , Yu, X. , and Liu, B. , 2008, “Turbulence Models Assessment for Large-Scale Tip Vortices in an Axial Compressor Rotor,” J. Propul. Power, 24(1), pp. 15–25. [CrossRef]
Scillitoe, A. D. , Tucker, P. G. , and Adami, P. , 2015, “Evaluation of Rans and Zdes Methods for the Prediction of Three-Dimensional Separation in Axial Flow Compressors,” ASME Paper No. GT2015-43975.
Liu, Y. , Yan, H. , Liu, Y. , Lu, L. , and Li, Q. , 2016, “Numerical Study of Corner Separation in a Linear Compressor Cascade Using Various Turbulence Models,” Chin. J. Aeronaut., 29(3), pp. 639–652. [CrossRef]
Liu, Y. , Yan, H. , Lu, L. , and Li, Q. , 2017, “Investigation of Vortical Structures and Turbulence Characteristics in Corner Separation in a Linear Compressor Cascade Using DDES,” ASME J. Fluids Eng., 139(2), p. 021107. [CrossRef]
Scillitoe, A. D. , Tucker, P. G. , and Adami, P. , 2017, “Numerical Investigation of Three-Dimensional Separation in an Axial Flow Compressor: The Influence of Freestream Turbulence Intensity and Endwall Boundary Layer State,” ASME J. Turbomach., 139(2), p. 021011. [CrossRef]
Yan, H. , Liu, Y. , Li, Q. , and Lu, L. , 2018, “Turbulence Characteristics in Corner Separation in a Highly Loaded Linear Compressor Cascade,” Aerosp. Sci. Technol., 75, pp. 139–154. [CrossRef]
Gourdain, N. , Gicquel, L. Y. , and Collado, E. , 2012, “Comparison of Rans and Les for Prediction of Wall Heat Transfer in a Highly Loaded Turbine Guide Vane,” J. Propul. Power, 28(2), pp. 423–433. [CrossRef]
Slotnick, J. , Khodadoust, A. , Alonso, J. , Darmofal, D. , Gropp, W. , Lurie, E. , and Mavriplis, D. , 2014, “CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences,” National Aeronautics and Space Administration, Washington, DC, Report No. NASA/CR-2014-218178. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140003093.pdf
Marble, F. E. , 1964, “Three-Dimensional Flow in Turbomachines,” High Speed Aerodyn. Jet Propul., 10(10), pp. 83–166.
Xu, L. , 2002, “Assessing Viscous Body Forces for Unsteady Calculations,” ASME Paper No. GT2002-30359.
Peskin, C. S. , 2002, “The Immersed Boundary Method,” Acta Numer., 11, pp. 479–517. [CrossRef]
Fadlun, E. , Verzicco, R. , Orlandi, P. , and Mohd-Yusof, J. , 2000, “Combined Immersed-Boundary Finite Difference Methods for Three-Dimensional Complex Flow Simulations,” J. Comput. Phys., 161(1), pp. 35–60. [CrossRef]
Defoe, J. J. , and Spakovszky, Z. S. , 2013, “Effects of Boundary-Layer Ingestion on the Aero-Acoustics of Transonic Fan Rotors,” ASME J. Turbomach., 135(5), p. 051013. [CrossRef]
Lieser, J. , Biela, C. , Pixberg, C. , Schiffer, H.-P. , Schulze, S. , Lesser, A. , Kähler, C. , and Niehuis, R. , 2011, “Compressor Rig Test With Distorted Inflow Using Distortion Generators,” 60 Deutscher Luft-und Raumfahrtkongress DGLRK2011-241449, pp. 1507–1516.
Niehuis, R. , Lesser, A. , Probst, A. , Radespiel, R. , Schulze, S. , Kähler, C. , Spiering, F. , and Kroll, N. , 2013, “Simulation of Nacelle Stall and Engine Response,” 21st International Society for Air Breathing Engines (ISABE) Conference, Busan, Korea, Sept. 9–13.
Übelacker, S. , Hain, R. , and Kähler, C. J. , 2016, “Flow Investigations in a Stalling Nacelle Inlet Under Disturbed Inflow,” Advances in Simulation of Wing and Nacelle Stall, Springer, Cham, pp. 271–283.
Wartzek, F. , Holzinger, F. , Brandstetter, C. , and Schiffer, H.-P. , 2016, “Realistic Inlet Distortion Patterns Interacting With a Transonic Compressor Stage,” Advances in Simulation of Wing and Nacelle Stall, Springer, Cham, pp. 285–302.
Fidalgo, V. J. , Hall, C. , and Colin, Y. , 2012, “A Study of Fan-Distortion Interaction Within the Nasa Rotor 67 Transonic Stage,” ASME J. Turbomach., 134(5), p. 051011. [CrossRef]
Barthmes, S. , Haug, J. P. , Lesser, A. , and Niehuis, R. , 2016, “Unsteady Cfd Simulation of Transonic Axial Compressor Stages With Distorted Inflow,” Advances in Simulation of Wing and Nacelle Stall, Springer, Cham, pp. 303–321.
Ma, Y. , Cui, J. , Vadlamani, N. R. , and Tucker, P. , 2018, “Effect of Fan on Inlet Distortion: Mixed-Fidelity Approach,” AIAA J., 56(6), pp. 2350–2360. [CrossRef]
Sirovich, L. , 1967, “Initial and Boundary Value Problems in Dissipative Gas Dynamics,” Phys. Fluids, 10(1), pp. 24–34. [CrossRef]
Sirovich, L. , 1968, “Steady Gasdynamic Flows,” Phys. Fluids, 11(7), pp. 1424–1439. [CrossRef]
Salathé, E. P. , and Sirovich, L. , 1967, “Boundary-Value Problems in Compressible Magnetohydrodynamics,” Phys. Fluids, 10(7), pp. 1477–1491. [CrossRef]
Goldstein, D. , Handler, R. , and Sirovich, L. , 1993, “Modeling a No-Slip Flow Boundary With an External Force Field,” J. Comput. Phys., 105(2), pp. 354–366. [CrossRef]
Cao, T. , Vadlamani, N. R. , Tucker, P. G. , Smith, A. R. , Slaby, M. , and Sheaf, C. T. , 2017, “Fan–Intake Interaction Under High Incidence,” ASME J. Eng. Gas Turbines Power, 139(4), p. 041204. [CrossRef]
Cao, T. , Hield, P. , and Tucker, P. G. , 2017, “Hierarchical Immersed Boundary Method With Smeared Geometry,” J. Propul. Power, 33(5), pp. 1151–1163. [CrossRef]
Watson, R. , Cui, J. , Ma, Y. , and Hield, P. , 2017, “Improved Hierarchical Modelling for Aerodynamically Coupled Systems,” ASME Paper No. GT2017-65223.
Bitter, M. , Wartzek, F. , Übelacker, S. , Schiffer, H.-P. K. , and Kähler, C, J. , 2015, “Characterization of a Distorted Transonic Compressor Flow Using Dual-Luminophore Pressure-Sensitive Paint,” Tenth Pacific Symposium on Flow Visualization and Image Processing (PSFVIP-10), fedOA (Federico II Open Archive), Naples, Italy, June 15–18.
Liu, Y. , Lu, L. , Fang, L. , and Gao, F. , 2011, “Modification of Spalart–Allmaras Model With Consideration of Turbulence Energy Backscatter Using Velocity Helicity,” Phys. Lett. A, 375(24), pp. 2377–2381. [CrossRef]
Tang, Y. , Liu, Y. , and Lu, L. , 2018, “Solidity Effect on Corner Separation and Its Control in a High-Speed Low Aspect Ratio Compressor Cascade,” Int. J. Mech. Sci., 142, pp. 304–321. [CrossRef]
Wartzek, F. , Brandstetter, C. , Holzinger, F. , and Schiffer, H. , 2015, “Response of a Transonic Compressor to a Massive Inlet Distortion,” European Turbomachinery Conference, Madrid, Spain, Mar.

Figures

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Fig. 2

Sketch of the Darmstadt rotor test case setup for validation

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Fig. 1

Hierarchy of turbulence and geometry modeling

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Fig. 3

Sketch of the test cases for varying (a) fan-locations and (b) beam heights

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Fig. 5

Prediction of wall-normal profiles of (a) mass flux and (b) total pressure at x = 4.5H using different meshes

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Fig. 6

Performance map of the Darmstadt Rotor: (a) massflow rate (kg/s, 100% RS) and (b) massflow rate (kg/s, 65% RS). SC represents smooth casing and B120 represents 120 deg beam.

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Fig. 7

Contours of (a) axial velocity distribution on the meridional plane and (b) total pressure distribution on the cross section at upstream of the rotor trailing edge at 100% speed

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Fig. 8

Separation region downstream the beam

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Fig. 4

Inflectional points of the separation bubble

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Fig. 17

Effect of different degrees of distortion on (a) mass flux and (b) total pressure ratio in the absence of fan

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Fig. 18

Effect of different degrees of distortion on (a) mass flux and (b) total pressure ratio. “Loc0” corresponds to the case with fan placed at x = 5.2H and “Duct” corresponds to the case without fan.

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Fig. 10

Circumferential variation of the total pressure ratio at the stage exit at 100% speed. Three radial locations are shown: (a) 10%, (b) 50%, and (c) 90% of the annulus height: (a) hub, (b) midspan, and (c) shroud.

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Fig. 11

Radial distribution of mass flux from IBMSG modeling and resolved cases

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Fig. 14

Recovery factor with varying (a) fan-locations x/H and (b) beam heights y/H

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Fig. 15

Q-isosurfaces (Q = 1 × 107) colored with axial velocity for different beam heights: (a) 1/2H, with fan and (b) 1/4H, with fan

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Fig. 16

Total pressure loss with increasing beam height

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Fig. 12

Q-isosurfaces (Q = 1 × 107) coloured with axial velocity for different fan-locations (a) x = 6.2H and (b) x = 7.2H

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Fig. 13

Effects of different blade locations on (a) mass flux and (b) total pressure ratio

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Fig. 9

Circumferential variation of the relative total pressure ratio at three axial stations: (a) rotor inlet, (b) rotor outlet, and (c) stator outlet at 100% speed, radially averaged by area

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